Abstract: A method is provided for an engine. During this method, a database is provided for a parameter of the engine. The database includes a plurality of values for the parameter determined over a period of time. Confidence bands are established using a probability density function on the database. An action is performed in response to a comparison of a first updated value for the parameter to the confidence bands. The engine may be configured as a gas turbine engine or another type of heat engine.

Abstract: There is provided a data access method and system for an aircraft. Password data is obtained for use in providing access to aviation data collected by at least one data acquisition device from one or more locations in the aircraft. The password data is caused to be rendered on at least one display provided in at least one secured location of the aircraft. Subsequent to the password data being rendered on the at least one display, input data is received from at least one user device requesting access to the aviation data. The input data is compared to the password data and, when the input data matches the password data, a connection is established between the at least one user device and the at least one data acquisition device for providing the at least one user device access to the aviation data.

Abstract: A data recording and transmission method and system for use in balancing a propeller of an aircraft. The method comprises operating the propeller in-flight, receiving, during operation of the propeller in-flight, vibration data associated with the propeller, retrieving, from a non-volatile memory on-board the aircraft, configuration data associated with the propeller, and transmitting the vibration data and the configuration data to a data processing device configured to determine a balancing solution for the propeller based one the vibration data and the configuration data.

Abstract: Methods and systems for assessing compliance of aircraft engines are described. The method comprises selecting a test population from a set of deployed aircraft engines based on one or more selection criteria, each of the deployed aircraft engines having associated thereto design requirements and field data; selecting at least one parameter that is present in both the design requirements and the field data of the test population, the design requirements comprising design time-series profiles, the field data comprising field time-series profiles; comparing the field time-series profiles to the design time-series profiles for the at least one parameter using a similarity metric to obtain field statistics; comparing the field statistics to expected statistics from the design requirements; and generating a compliance assessment output of the test population based on a difference between the field statistics and the expected statistics.

Abstract: There is provided a data tracking method and system for an aircraft having one or more engines. The method comprises reading, by a mobile device, at least one computer-readable label associated with at least one of one or more engine modules of the one or more engines and one or more Line Replaceable Units (LRUs) of at least one of the aircraft and the one or more engines to obtain label information having encoded therein at least one of engine module data uniquely identifying each engine module and LRU data uniquely identifying each LRU, extracting, on the mobile device, the at least one of the engine module data and the LRU data from the label information, and transmitting the at least one of the engine module data and the LRU data from the mobile device to a data transmission unit provided on-board the aircraft.

Abstract: There is provided a method and a system for propeller balancing of an aircraft. The method comprises operating a propeller in-flight, receiving propeller vibration data during operation of the propeller in-flight, computing, after at least one flight of the aircraft, an average vibration magnitude and an average vibration phase angle based on the propeller vibration data, determining a propeller balancing solution based on the average vibration magnitude and the average vibration phase angle, and generating a balancing need indication by outputting the propeller balancing solution.

Abstract: A data recording and transmission method and system for use in balancing a propeller of an aircraft. The method comprises operating the propeller in-flight, receiving, during operation of the propeller in-flight, vibration data associated with the propeller, retrieving, from a non-volatile memory on-board the aircraft, configuration data associated with the propeller, and transmitting the vibration data and the configuration data to a data processing device configured to determine a balancing solution for the propeller based one the vibration data and the configuration data.

Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.

Abstract: The present disclosure provides methods and systems for propeller balancing of an aircraft comprising a propeller. Acceleration data is obtained from an acceleration sensor coupled to the aircraft. The acceleration data is filtered using a filter to obtain propeller-specific vibration data, the filter defining a range of acceptable frequencies associated with a frequency of rotation of the propeller. The propeller-specific vibration data is compared to trend data associated with the propeller. When the propeller-specific vibration data differs from the trend data beyond a predetermined threshold, an alert indicative of a balancing need for the propeller is issued.

Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.

Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.

Abstract: There is described herein a propeller balancing system and method that determines a stable cruise condition of an aircraft during flight, and considers vibration data for propeller balancing collected while the aircraft is in the stable cruise condition. Parameters used to determine stable cruise condition may be unique for each flight and/or aircraft, and balancing solutions may be determined based on these unique parameters.